Mars Lander

Science Payload & Advanced Concepts OfficeDirectorate of Science Page 1Mars Express Workshop, 25 Feb. 2005

On the feasibility of a fast track return to Mars

Mars Lander(s) 2011Mars Demonstration Landers (MDL)


Entry, Descent and Landing

SMART 1 Solar Electric Propulsion

BepiColomboMercurySolo

OrbiterCosmic Vision2015-2025

Technology Demonstrators

SMART 2LISA PF

Drag FreeControl

LISAMercuryCosmic Vision

2015-2025

Mars Moon Mercury Europa


What are the descent options ?1. Passive Descent: Parachute System with Airbags on Landing

(High risk and applicable only to Mars)

2. Powered Descent: Thrusters (+Parachute System when applicable) (Horizontal and Vertical Velocity Control)

Soft Landing significantly reduce risk at impactVery high mass descent systemTechnology learning curve can be applied to airless bodies

3. Partially Controlled Descent: Parachute System + Thrusters (Horizontal Velocity Control) with Airbags on Landing

Reduce horizontal velocity reduce risk at impactHigher mass system


1) Passive Descent• Higher Risk as no control is

implemented on descent• European Heritage - from

Huygens Entry & Descent System– Similar to Mars entry since

Huygens was deployed at a very high altitude where atmospheric density is similar to that encountered on Mars

– Learning curve from Beagle 2• Over-dimension EDLS• Extensive ground test and

verification programme• Telemetry during descent

Huygens Descent Profile


2) Powered Descent (Soft Landing)

• Reduction in velocity for landing reduces riskBut….

• NO HERITAGE IN ESA or Member States– Time constraints for an early launch in the 2011 window do

not permit the development of a powered descent system• Design phase (including learning curve from other agency’s• Extensive test and validation phase

• Extremely mass constraining• Key long term technology for Moon/Mercury/Europa


3) Partially Controlled Descent• Provides Horizontal & some vertical Velocity Control• Reduces Risk on Landing

– Optimizes conditions for airbag impact

• No Technology Heritage in Europe Immediate Developments Required

– Control Sensors– Thrusters– Airbags/parachutes/GNC/ System development


MDL- A Possible Descent Profile

From Aurora Demo Lander Study


Airbags• Permits Hard Landing

– both Passive and Controlled Descents• Limited heritage in Europe

– Immediate Development Required– Extensive ground test campaign required

• Airbags must be released or retracted so as not to impede Lander after impact– Vented & sealed airbag tradeoff


Selection of MDL Landing Sites• Landing Site Selection is Critical to Ensure Successful Descent

and Landing of the MDL’s• Elevation limited due to the requirement for a thick enough

column of atmosphere to allow sufficient deceleration and safe landing– MER A, MER B, elev. < -1 km & Viking 1 /2, elev.< -3km)– Lower landing elevation leads to greater margin in EDLS (but may bias

science)• Latitude limited by power requirements

– constrained by use of solar cells– preliminary limit : -35 deg to +35 deg

• Landing sites should be scientifically important for– Exobiology– Geophysics


Current or Attempted Landing Sites

MTL limit

MTL limit


Possible Payloads (1): Beagle 2Instrument Mass [g] Power [W]Gas Analysis Package 5740Environmental Sensor 0.156Two Stereo Cameras 350 1X-ray spectrometer 154 3.9Microscope 205Mössbauer Spectrometer

540 3

Rock Corer Grinder 348 6PLUTO (incl. deployment unit)

890 3

Total 8.2 kg

Payload available ~ 10 kg


Possible Payload (2) : Netlander PayloadInstrument Mass

[g]Power [W]

Status

ATMIS: Atmospheric Sensors 855 0.43 BeadboardSEISMO: Seismometer (VBB+SP)

1700 0.5 Breadboard

PANCAM: Panoramic Camera (incl. boom)

1860 Breadboard

ARES (ELF): Electric Field 100 0.3 Study?MAG: Magnetometer 210 0.25 Flight unitGPR: Ground Penetrating Radar

460 Study

Microphone 50NEIGE: Ionosphere & Geodesy Experiment

300

SPICE: Soil Properties 50 BreadboardTotal 5.6 kg

Payload available ~ 10 kg


Possible Payload (3): Sub-surface sampler

• Mole available by 2011– Can be configured for geophysics or exobiology

• Mole carrying the HP3 (Heat Flow and Physical Properties Package)– HP3-TEM (Thermal Excitation and Measurement Suite)– HP3-DEN (Densitometer)– HP3-DACTIL (Depth, Accelerometry and Tilt Measurements)

• Mole carrying exobiology package– ATR (Attenuated Total Reflection Spectroscopy)– Optically stimulated Luminescence dating– Raman spectrometer


The only way is down

PLUTO ISM

Purpose Sample Collection Instrument CarrierRetrievable Yes NoP/L No YesMass, Power, Size 890 g, 3 W, 280x20mm 1110 g, 3W, 330x25mmPenetr. Depth [m] 1.5 5Penetr. Speed 1.5 m in 1.16 h 5 m in 5.7 hStatus Flight Model (Beagle 2) Functional and tested

Breadboard in 2005

Comparison between PLUTO and the new Instrumented Mole System (ISM)


Subsurface Measurements

HP3 ATR

X

X

X

active dev.BB in 2006

µRaman XRS

XX

X

study

Phys. Prop.

MineralogyChemistryExobiology

Development Status

Instrument Packages for the ISM

HP3 – Heat Flow Physical Properties PackageATR – Attenuated Total Reflection Spectroscopy

µRaman – Front end in ISM, main instrument on LanderXRS – X-ray spectrometer


Mars Demonstration Lander Study Heritage• Two relevant studies

– D-Sci Mars Network Science study (4 Landers, 92 kg with improved EDLS, hyperbolic insertion)

– Aurora Mars Demo Lander (1 Lander 250 kg, partial controlled descent, hyperbolic insertion)

• Mars Network Science Study looked at the re-use of MEX technology to deliver a set of Landers to Mars & provide communications. Limited study of EDLS & Landers


Mars Demonstration Lander Proposed Approach• Top level assumptions

Soyuz Fregat SF2b from KourouLaunch to Highly Elliptical Orbit prior to Earth Escape

(to maximize mass)Adapted and Optimized MEX carrier

Provide communications relay and possible orbiter P/L• Lander assumptions

for 2 Landers, ~150 kg eachReleased from Mars elliptical orbit (comm. during descent)40 kg surface element including a 10 kg payloadDesign significant margins to over-dimension the EDLS Communications during descent and landingLanders released independently in a phased manner to two different landing sites

• 2 Landers Increases probability of a successful landingIncreased landing test dataIncreased Science return (consider subsurface science)

Study needs to be conducted urgently to ensure schedule !


Mars Demonstration Lander Status & Needs• Status:

– No demonstrated European capability of a safe landing on high-gravity planetary body with low atmospheric density

– Demonstration required of the EDLS before taking the next logical steps for any strategic phased exploration programme

• Surface networks• Surface mobility• Deep subsurface studies

– Improved Lander (Beagle 2/NetLander-class) is logical first step• Development needs:

– Robust system with partial descent control, to cope with the uncertain environment (pressure, temperature, wind, terrain)

– Telemetry of critical EDLS parameters during Descent & Landing– Consolidate end-to-end European EDLS, with priorities (in order):

• Airbags, Descent Thrusters and GN&C, Parachutes, Front Shield, • System validation (qualification, test & analysis) over a wide range of

external parameters


Mars Demonstration Lander Development NeedsItem Needs

Spin-up & Eject Mechanism

• Increased accuracy • Huygens-derived design, with lower mass

Back Cover • Increase in size Front Shield • Increase in size Parachutes • Optimisation and test Thrusters • Thrusters for velocity control during descent GN&C • Camera and Radar or LIDAR for descent control Airbags • Optimised sizing and pressure

• Inflation, drop, long-term storage testing • European development • Russian expertise (Netlander connection) may be exploited

EDLS

System Validation & Testing

• EDLS Analysis and Test • Analysis and delta testing of all mechanisms • Software independent validation • End-to-end functional testing on ground model

Structure • Increased size, ruggedisation and repackaging Power • Larger batteries and battery charging (Tx powered during

descent, Rx permanently powered) Avionics • Redundant electronics to improve overall system reliability

• External antenna for transmission during descent

Surface Module

Payload • Additional European instruments (sub-surface package) • Core payload (on both landers) plus add-ons


Mars Demonstration Lander Mission

• Launch: November 2011 (Backup 2013)• Intermediate Earth HEO

Provides Increase in Available S/C + Lander(s) Mass

• Ballistic Mars Transfer (transfer time ~ 10 months)• Mars Elliptical Orbit

Needs optimization for mass/communications/powerLander(s) will be released in a phased manner from Orbit

– Reduce Entry Velocity– Better Control of Entry Conditions– Ability to Analyze Atmosphere Prior to Descent.– Orbit Insertion in Good Weather– Permit Communication During Descent and Landing


Mars Demonstration Lander : S/C Orbiter Design

• Mars Express Heritage– Propulsion Subsystem– Thermal Subsystem– Avionics and Data Handling– Power Subsystem (with updated

solar array – (increased efficiency low mass)

• New Design– Adapted Structure for 2 Landers

• Other– Tanks

From Mars Network Science Study (D-SCI)


Recommendations from Beagle 2 Inquiry Board

• Robust Design Margins• Telemetry during critical phases

(entry, descent,..)• Stringent testing process for all systems

(parachutes, airbags, release mechanisms, etc.)• Redundancy for entry detection event• …


Immediate Steps and Development

• Detailed consistent Lander study with Technology Development Plan (TDP)

Start ASAP, Complete by Q4 2005

• Key TDP items to initiate now:– Airbag System– Controlled Descent System


Activities & Schedule (Launch in 2011)


Conclusion

• A European Lander Mission to Mars appears:– Doable in 2011 provided work start immediately– Could prepare the road for larger European endeavors to

Mars – Rovers, deep subsurface studies– Would provide serious Martian scientific return– Could sample subsurface down to 5 m

• The Mars Demonstration Lander would allow:– A phased technology development for future Mars exploration– Longer term spin-off on other science missions– Important step for ESA Science, Exploration & Technical

Directorates

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Mars Lander